Abstract: Methods, systems, and apparatus for controlling a turbine clearance in an aircraft engine are provided. A method includes activating a turbine clearance control based on a flight phase of an aircraft using the aircraft engine, and adjusting the turbine clearance based on a preselected turbine clearance value.

Abstract: Methods, systems, and apparatus for controlling a turbine clearance in an aircraft engine are provided. A method includes activating a turbine clearance control based on a flight phase of an aircraft using the aircraft engine, and adjusting the turbine clearance based on a preselected turbine clearance value.

Abstract: A gas turbine engine combustor includes outer and inner liners joined together at an annular dome. Outer and inner air swirlers and cooperating fuel injectors are mounted in two rows in the combustor dome. The fuel injectors are joined to a common fuel manifold for simultaneously channeling fuel thereto over an operating range from idle to full power for reducing exhaust emissions.

Abstract: A gas turbine engine combustor is provided with a combustor dome plate film cooling means having an annular slotted ring to provide a film starting means upstream of a multi-hole film cooled single wall metal dome plate which is annular in shape. One particular embodiment provides a starting slot in the form of a plurality of rings surrounding the edges of the air/fuel nozzle inlet apertures in the dome plate. The cooling holes are disposed in concentric circles about the apertures and angled along radii emanating from the center of the apertures. This produces a cooling film emanating radially from the ring like circular slots around each air/fuel nozzle inlet aperture in the dome plate. Another embodiment provides a starting slot in the form of circumferential rails circumferentially disposed about the inner and outer circumferential edges of dome plate.

Abstract: A method of diluting combustion gases in a gas turbine engine combustor includes injecting primary dilution air into the combustion gases, and injecting trim dilution air into the combustion gases adjacent to the injected primary dilution air. A dilution air injector for practicing the method includes a plate, or centerbody in an exemplary embodiment, having a primary dilution hole for injecting a portion of compressed air into combustion gases as primary dilution air, and a trim dilution hole for injecting a portion of the compressed air into the combustion gases as trim dilution air. The primary and trim dilution holes are sized and configured so that the primary and trim dilution air cooperate with each other for penetrating into and diluting a predetermined portion of the combustion gases.